CN103221200B - Method and device for producing large cylindrical structures - Google Patents
Method and device for producing large cylindrical structures Download PDFInfo
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- CN103221200B CN103221200B CN201180055371.4A CN201180055371A CN103221200B CN 103221200 B CN103221200 B CN 103221200B CN 201180055371 A CN201180055371 A CN 201180055371A CN 103221200 B CN103221200 B CN 103221200B
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- tension rope
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- 238000000034 method Methods 0.000 title claims abstract description 29
- 239000000835 fiber Substances 0.000 claims abstract description 32
- 238000004519 manufacturing process Methods 0.000 claims abstract description 28
- 229920002430 Fibre-reinforced plastic Polymers 0.000 claims abstract description 8
- 239000011151 fibre-reinforced plastic Substances 0.000 claims abstract description 8
- 238000000465 moulding Methods 0.000 claims abstract description 8
- 239000004033 plastic Substances 0.000 claims abstract description 8
- 229920003023 plastic Polymers 0.000 claims abstract description 8
- 239000000463 material Substances 0.000 claims description 17
- 239000011265 semifinished product Substances 0.000 claims description 13
- 238000004804 winding Methods 0.000 claims description 5
- 238000001816 cooling Methods 0.000 claims description 2
- 239000002657 fibrous material Substances 0.000 abstract 2
- 229910000831 Steel Inorganic materials 0.000 description 10
- 239000010959 steel Substances 0.000 description 10
- 238000003483 aging Methods 0.000 description 7
- 238000007493 shaping process Methods 0.000 description 5
- 230000002787 reinforcement Effects 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 239000000945 filler Substances 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000000087 stabilizing effect Effects 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 230000004308 accommodation Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 239000004918 carbon fiber reinforced polymer Substances 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 238000005025 nuclear technology Methods 0.000 description 1
- 238000013404 process transfer Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000004575 stone Substances 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
- 229920001187 thermosetting polymer Polymers 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/02—Moulds or cores; Details thereof or accessories therefor with incorporated heating or cooling means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/20—Opening, closing or clamping
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/20—Opening, closing or clamping
- B29C33/202—Clamping means operating on closed or nearly closed mould parts, the clamping means being independently movable of the opening or closing means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/44—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles
- B29C33/48—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling
- B29C33/485—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling cores or mandrels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
- B29C45/17—Component parts, details or accessories; Auxiliary operations
- B29C45/26—Moulds
- B29C45/261—Moulds having tubular mould cavities
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
- B29C45/17—Component parts, details or accessories; Auxiliary operations
- B29C45/64—Mould opening, closing or clamping devices
- B29C45/641—Clamping devices using means for straddling or interconnecting the mould halves, e.g. jaws, straps, latches
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
- B29C70/462—Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
- B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3082—Fuselages
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
- Y10T156/10—Methods of surface bonding and/or assembly therefor
- Y10T156/1002—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina
- Y10T156/1028—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina by bending, drawing or stretch forming sheet to assume shape of configured lamina while in contact therewith
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention relates to a method for producing large cylindrical structures or large cylindrical molded parts (F), in particular fuselage parts for aircraft manufacture made of fiber-reinforced plastic, wherein fibers, preferably semi-finished fiber materials (4), and a curable plastic mass (5) are introduced into a molding space (3) between an inner cylindrical mold (1) and an outer cylindrical mold (2) and then cured. Said method is characterized in that the inner cylindrical mold (1) is made up of a plurality of inner segments (1a) distributed about the circumference, and the outer cylindrical mold (2) is made up of a plurality of outer segments (2a) distributed about the circumference, and that the outer segments (2a) are braced against the inner mold (1) by means of one or more tension cables (8) which are wound about the outer segments (2), interposing the fibers or semi-finished fiber material (4).
Description
Technical field
The present invention relates to a kind of method for being manufactured columniform large scale structure or large-scale moulded parts, body element especially for aircraft manufacturing by fibre-reinforced plastics, in the die cavity wherein between columniform internal mold and columniform external mold, load plurality of fibers, preferred one or more fibre semi-finished products and introduce plastic material age-hardenable.And then age-hardening plastic material.Plastic material is generally the thermoset plastic material for the manufacture of fibre-reinforced plastics and therefore fibrous composite.Each fiber is imbedded in plastic substrate by this.Fiber can be such as glass fibre and/or carbon fiber, but also can be other fiber type.Each fiber sporadically can exist but preferably exist as fiber mat or similarity piece using half-finished form.Large scale structure or large-scale moulded parts refer specifically to the cylindrical moulded parts of diameter at least 2m, preferably at least 3m.Large scale structure or large-scale moulded parts can be particularly preferably the body element for aircraft manufacturing.
Background technology
Known, prefabricated particularly tubular, particularly barrel-shaped each frame sections and the airframe be assembled in back to back final assembling respectively in the manufacture of airframe.Fibrous composite, such as carbon fiber reinforced plastics (CFK) are day by day used as material.The airframe with high stability and simultaneously little weight can be manufactured in such a way.
By a kind of known method for the manufacture of tubular-shaped structures component of DE 10 2,007 060 029 A1, wherein provide tubular mould, it has the mold surface of shaping corresponding with the outer surface of structural elements.Mold surface is made up of expandable carrier, and it is shaped like this, and namely mould fills up to when the expansion spacing of die surface when retaining bearing-surface by it under unexpanded state.Carrier is arranged in a mold and is pressed onto on die surface by fibre core by the expansion of carrier.And then matrix impregnates fibre core age-hardenable is utilized.
In order to the body element of automated manufacturing such as aircraft manufacturing, suggestion uses the coil winding machine for fibre semi-finished products (see US 7 048 024 B2) of automation in addition.
By the field of container technique in accumulator, such as also known in the accumulator of nuclear technology equipment, accumulator installs pre-tightening apparatus in outside, pre-tightening apparatus reels with coiler device with each pretension element (see DE 27 16 020) of the form of rope, and the structure of such exploitation on the body element of such as aircraft manufacturing does not affect.
Summary of the invention
The object of the invention is to, a kind of method is provided, large scale structure or large-scale moulded parts, body element especially for aircraft manufacturing can be manufactured by economic mode with high quality by fibre-reinforced plastics by means of it.
In order to reach this object, in the method for same for the manufacture of large scale structure or large-scale moulded parts, the present invention advocates, columniform internal mold is made up of multiple circumferential interior sector and external mold is made up of multiple circumferential outer sector, and by tight for inside for outer sector die clamp when utilizing one or more tension rope reeled around outer sector to arrange fiber or fibre semi-finished products outside between sector and internal mold.
To this present invention first from such opinion, if namely internal mold is made up of multiple interior sector, thus by they can in a simple manner " inwardly " remove, then the large scale structure that can take out after shaping in a simple manner or large-scale moulded parts.This particularly has advantage when having material (the shrinking in its process in age-hardening) of negative temperature coefficient, namely realizes the simple demoulding of component.But external mold is also made up of multiple circumferential outer sector, thus realize the manipulation of improvement again.Still the large power produced can be received in shaping or age-hardening process in a simple manner, because external mold is clamped by towards internal mold by means of the tension rope reeled around external mold in such form of implementation.Realize the simple structure of mould, the simple manufacture of mould and the particularly also simple taking-up of mould or the simple demoulding of component that completes thus.
Preferably first form internal mold by multiple interior sector, and then fiber or at least one fibre semi-finished products are added to be located at and be wound up on internal mold on internal mold, such as.Then place and assemble external mold in other words and by means of tension rope, external mold clamped.Finally moulding material added, be such as injected in die cavity.Object is met to this, before shaping and/or regulate the temperature of mould in process, preferably heat.Then moulding material age-hardening when fiber embeds.
Consider such fact, namely the fuselage of such as aircraft is generally provided with multiple fastening element, the present invention is suggestion in preferably forming further, also preferably also multiple fastening element such as reinforcement, rib or similarity piece is installed on internal mold before adding fiber or fibre semi-finished products outside before module dress.Therefore internal mold also generally has multiple groove as the accommodation section for fastening element on its outer surface towards external mold in forming surface for this reason.The reinforcement that fastening element such as can be bending rib and/or extend along the longitudinal direction.These fastening elements (it is common in aircraft manufacturing) can be incorporated in a simple manner according in manufacture process of the present invention in a manner described.
In order to the moulded parts taken out from mould, the present invention advises further, first removes internal mold, and its mode is for preferably radially to draw each single interior sector in.Meet object for this reason, each interior sector is separated from one another and then inwardly overturn to a certain extent on its end face mutually reclined.Each interior sector (or multiple interior sector) can connect alternatively mutually with deflecting, but also can be made up of multiple part.Preferably form the end face mutually reclined or the interface of each sector like this at this, make to form a stable structure in the assembled state, it sustains the pressure of clamped external mold.Can object be met for this reason, load stabilizing member between each interior sector in the end loaded in the assembling process of internal mold, such as, stablize wedge, stablize filler rod etc.First stabilizing member is removed in knockout course, thus then can inwardly overturn each interior sector simply.
Such possibility is there is in a form of implementation changed, namely, each single interior sector is fixed on the collecting device of an automation jointly, by means of this collecting device via one or more applicable the drive unit simultaneously or in turn radially inside each single interior sector of tractive.Such collecting device such as can have the support at center or the wheel hub at center, each interior sector by its with the connecting rod arranged between the support at center or the wheel hub at center with the support at center or the hub hinged at center be connected.Then can the inside each single interior sector of tractive via each connecting rod by the rotation of the support at center.Via each connecting rod radially directed in the fabrication process, also larger power can be born.
Particularly above-mentioned tension rope, such as steel cable are wound up on the external mold of assembling within the scope of the invention.Usually coiler device is set for this reason.The mould particularly preferably assembled in order to the tension rope own rotation that reels, and launches tension rope from a rope capstan winch or from multiple rope capstan winch simultaneously.Avoid in such a way and heavy rope capstan winch is carried large displacement around static mould.But rope capstan winch can be arranged position regularly.Generation make mould be in rotation by means of the drive unit be applicable to, thus tension rope is by unwinding and winding.
Target of the present invention is also a kind of equipment, and it is for manufacturing columniform large scale structure or large-scale moulded parts, body element especially for aircraft manufacturing by a kind of method of the above-mentioned type.This equipment has the internal mold be made up of multiple interior sector and the external mold be made up of multiple outer sector within the scope of the invention.Coiler device is also set for the tension rope that reels to external mold.Coiler device preferably has one or more rope capstan winch, from it unwinding or expansion rope.Simultaneously coiler device preferably has the swinging strut for mould, to be wherein fixed to by mould or to be fixed on this swinging strut and pillar is configured with the unwind process transfer moving mold that rotating driving device is used at steel cable.
For the ease of rope to be wound up on external mold or outer sector and to guarantee uniform clamping; the present invention's suggestion in preferred formation further; external mold or its each outer sector have in outside at least one spirality around groove or rill, tension rope embeds in described groove or rill in winding process or tension rope guides in groove or rill.
Internal mold and/or external mold or their each sector are preferably configured with multiple heat tunnel and/or multiple cooling duct, for regulating the temperature of mould before age-hardening and/or in period.This outer mold is configured with multiple applicable feed path, moulding material age-hardenable can be introduced such as being expelled in die cavity via feed path.The supply of shaped material is particularly preferably embodied as via internal mold.Can make multiple radially directed feed path in internal mold, they pass into die cavity for this reason.These feed paths are connected to corresponding mixing head or shower nozzle, and these mixing heads or shower nozzle can be placed on internal mold in inner side.
Large scale structure or large-scale moulded parts, body element especially for aircraft manufacturing is manufactured by fibre-reinforced plastics economically in a simple manner within the scope of the invention generally with high-quality.
Accompanying drawing explanation
Below by only illustrating that the accompanying drawing of an embodiment illustrates in greater detail the present invention.Wherein:
Fig. 1 partly illustrates the internal mold for the manufacture of the body element for aircraft manufacturing, comprises point combo of insertion,
The object of Fig. 2 Fig. 1, multiple fastening element with insertion and the fibre semi-finished products added,
Fig. 3 has the complete internal mold of multiple fastening element in the half-finished process of coiled fiber,
Fig. 4 presses the object of Fig. 2, has the external mold of installation and part around upper steel cable,
The mould that Fig. 5 is whole and part around upper steel cable (corresponding to Fig. 4),
Fig. 6 presses the end-view of object when removing the beginning of internal mold of Fig. 5,
Fig. 7 presses the end-view of object in the process removing internal mold of Fig. 6,
Fig. 8 presses the perspective view of object in the process removing external mold of Fig. 7,
First view of Fig. 9 coiler device,
Second view of Figure 10 coiler device, and
The form of implementation (Local map) that Figure 11 a, b, c of the present invention changes.
Detailed description of the invention
Utilize the method shown in figure or utilize the equipment shown in figure can be manufactured the body element of columniform large scale structure, such as aircraft manufacturing by fibre-reinforced plastics.
Mould for the manufacture of such large scale structure comprises internal mold 1 and external mold 2, wherein between internal mold and external mold, forms die cavity 3.Fibre semi-finished products 4 is set in die cavity 3 and then plastic material 5 age-hardenable is loaded in die cavity 3 as matrix to manufacture moulded parts.
To be made up of multiple circumferential interior sector 1a according to internal mold 1 of the present invention and external mold 2 is made up of multiple circumferential outer sector 2a.
Observation by the comparison of Fig. 1 to 5 can illustrate the assembling of mould and the manufacture of moulded parts.
Fig. 1 first only partly illustrates that internal mold 1 illustrates an interior sector 1a in other words in the section of perspective.Can find out that this interior sector is provided with multiple groove 6, fastening element 7a, 7b can be inserted wherein.Fastening element is on the one hand the reinforcement 7a that extends along cylindrical longitudinal aspect and is bending and the rib 7b therefore along the circumferential direction extended on the other hand.
Insert after in each groove 6 at each fastening element 7a, 7b, add and the upper fibre semi-finished products 4 that preferably reels.This is shown by the observation of the comparison of Fig. 2 and 3.
After fibre semi-finished products 4 reels completely, install external mold 2, it is made up of multiple outer sector 2a.Then to reel multiple tension rope 8 around external mold 2, that is when arranging fibre semi-finished products 4 by means of each tension rope between external mold and internal mold, external mold 2 is clamped to internal mold 1.Figure 4 and 5 are at this tension rope 8 on the mould comprising internal mold 1 and external mold 2 shown in different views and winds portions.
Plastic shaping material 5 can be expelled in die cavity 3 after clamping external mold 2 to internal mold 1 completely.This is represented by arrow 5.
Can find out, in order to introduce moulding material, internal mold 1 is provided with multiple (radial directed) passage 9, and they are connected to again each shower nozzle or each mixing head 10.Shower nozzle or mixing head 10 are placed on internal mold 1 in inner side simultaneously.
Before moulding material age-hardening and/or period, regulate the temperature of internal mold 1 and/or external mold 2.Not only internal mold 1 but also external mold 2 are provided with multiple heat tunnel 11 for this reason, and they extend along cylindrical longitudinal direction in this embodiment.Heat tunnel for internal mold 1 is only shown.Regulated by temperature, moulding material 5 age-hardening when fiber or fibre semi-finished products 4 embed, thus form large-scale moulded parts such as body element to be manufactured.
In order to the moulded parts F that can take out from mould, preferably first remove internal mold 1.This is found out by the observation of the comparison of Fig. 6 to 8.
Can find out in Fig. 6, first in two adjacent sector 1a two docking points between take out locking wedge or locking filler rod 12, it also can be called top block or locking stone, thus radially-inwardly folding internal mold can being taken out (Fig. 7) to a certain extent.And then external mold 2(is turned on see Fig. 8), it is made up of two sector 2a in this embodiment, thus the moulded parts F that can take out.
The winding of tension rope 8 has special importance within the scope of the invention.The present invention provides coiler device 13 in order to be wound up on external mold 2 by steel cable in preferably improving one for this reason.This coiler device has two rope capstan winches 14 in an illustrated embodiment, launches steel cable 8 from it.In addition coiler device 13 has the whirligig 15 for mould, and this mould is made up of internal mold 1 and external mold 2.This whirligig 15 or swinging strut are provided with rotating driving device 16.Therefore in order to be wound up on external mold 2 by steel cable 8, mould 1,2 is rotated by means of whirligig 15, thus from unwinding steel cable 8(each rope capstan winch 14 especially see Fig. 9 and 10).
In order to ensure being wound up into by steel cable on external mold 2 faultlessly, external mold 2 is provided with multiple groove or rill 17, and it is the rill 17 that spirality is arranged on the excircle of external mold 2 in this embodiment.Can move along the longitudinal direction L of mould, tension rope can be reeled step by step at this capstan winch 14 of respectively restricting.
In addition manifold internal mold 1 has special importance within the scope of the invention, because can realize the simple demoulding of component by the gathering of internal mold 1.By Fig. 6 to 8, first form of implementation is described.Figure 11 a, 11b, 11c illustrate the form of implementation of change.
In this form of implementation, each interior sector 1a is connected to the collecting device 18 of an automation.This collecting device has the support at a center or the wheel hub 19 at center, each interior sector 1a by its with the connecting rod 20 arranged between the support at center or the wheel hub at center with the support at center or the hub hinged at center be connected.The observation of the comparison of Figure 11 a, 11b, 11c shows, automatically can retract each interior sector 1a by the rotation of the wheel hub 19 at center.
Utilize the equipment of method and the description described preferably to manufacture diameter to be greater than 3m, to be particularly preferably greater than the large scale structure of 4m.Internal mold and/or external mold preferably have that to be greater than 50mm, to be preferably greater than 80mm be such as the wall thickness of 100mm or larger under these circumstances.Tension rope is preferably steel cable, and it can have, and to be greater than 10mm, to be preferably greater than 20mm be such as the diameter of 30mm or larger.
Claims (12)
1. manufactured a method for columniform large scale structure or large-scale moulded parts (F) by fibre-reinforced plastics, wherein load fiber and plastic material age-hardenable (5) being arranged in the die cavity (3) between columniform internal mold (1) and columniform external mold (2); It is characterized in that, columniform internal mold (1) is made up of multiple circumferential interior sector (1a), and external mold (2) is made up of multiple circumferential outer sector (2a), and when utilizing one or more tension rope (8) reeled around outer sector (2) that fiber or fibre semi-finished products (4) are set between sector and internal mold outside, outer sector (2a) is clamped to internal mold (1).
2. in accordance with the method for claim 1, it is characterized in that, first internal mold (1) is formed by multiple interior sector (1a), and then fiber or at least one fibre semi-finished products (4) being added is located on internal mold (1), then assemble external mold (2) and by means of tension rope (8), external mold clamped, and finally moulding material (5) being loaded in die cavity (3).
3. according to the method described in claim 1 or 2, it is characterized in that, before external mold (2) assembling, multiple fastening element (7a, 7b) is arranged on internal mold (1).
4. according to the method described in claim 1 or 2, it is characterized in that, in order to moulded parts (5) demoulding made, first radially drawn in by internal mold (1), its mode is for by separated from one another for sector in each (1a) and/or deflect toward each other.
5. according to the method described in claim 1 or 2, it is characterized in that, in order to reel and tensioning tension rope (8), rotate assembling mould (1,2) and simultaneously from unwinding tension rope (8) at least one rope capstan winch (14).
6. according to the method described in claim 1 or 2, it is characterized in that, large scale structure or large-scale moulded parts (F) are the body element for aircraft manufacturing.
7. one kind is manufactured the equipment of columniform large scale structure or large-scale moulded parts by fibre-reinforced plastics according to the method as described in one of claim 1 to 6 item, comprise the internal mold (1) be made up of multiple interior sector (1a) and the external mold (2) be made up of multiple outer sector (2a), and comprise coiler device (13) for the external mold (2) that reels with tension rope (8).
8. according to equipment according to claim 7, it is characterized in that, coiler device (13) has one or more rope capstan winch (14), can unwinding tension rope (8) from this rope capstan winch.
9. according to the equipment described in claim 7 or 8, it is characterized in that, coiler device (13) has the swinging strut (15) for mould (1,2), on swinging strut (15), wherein connects rotating driving device (16) in order to rotate mould (1,2).
10. according to the equipment described in claim 7 or 8, it is characterized in that, external mold (2) or its each sector (2a) have in outside at least one spirality around groove or rill (17), in winding process, tension rope (8) embeds in described groove or rill.
11., according to the equipment described in claim 7 or 8, is characterized in that, internal mold (1) and/or external mold (2) are provided with multiple heat tunnel and/or cooling duct.
12., according to the equipment described in claim 7 or 8, is characterized in that, internal mold is provided with the collecting device (18) of automation, and interior sector (1a) can by the demoulding of drawing in for component by means of this collecting device.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102010051739A DE102010051739B3 (en) | 2010-11-19 | 2010-11-19 | Method and device for producing cylindrical large structures |
| DE102010051739.9 | 2010-11-19 | ||
| PCT/EP2011/070212 WO2012066017A1 (en) | 2010-11-19 | 2011-11-16 | Method and device for producing large cylindrical structures |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103221200A CN103221200A (en) | 2013-07-24 |
| CN103221200B true CN103221200B (en) | 2015-07-15 |
Family
ID=44999771
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201180055371.4A Expired - Fee Related CN103221200B (en) | 2010-11-19 | 2011-11-16 | Method and device for producing large cylindrical structures |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US9180638B2 (en) |
| EP (1) | EP2640567B1 (en) |
| CN (1) | CN103221200B (en) |
| DE (1) | DE102010051739B3 (en) |
| WO (1) | WO2012066017A1 (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2660031B1 (en) * | 2010-12-27 | 2020-03-25 | Kawasaki Jukogyo Kabushiki Kaisha | Molding jig and molding method |
| AT512362A1 (en) * | 2012-01-13 | 2013-07-15 | Ifw Manfred Otte Gmbh | Mold for a tool and the tool formed therefrom |
| DE102012202653A1 (en) * | 2012-02-21 | 2013-08-22 | Zf Friedrichshafen Ag | Method for producing fiber-reinforced plastic component, involves forming cavity between primary molding tool portion and secondary molding tool portion, injecting resin into cavity and removing plastic component |
| FR3015346B1 (en) * | 2013-12-19 | 2016-06-24 | Aerolia | METHOD FOR MANUFACTURING AN AIRCRAFT FUSELAGE PIECE, FUSELAGE PIECE OBTAINED BY SUCH A METHOD AND AN AIRCRAFT EQUIPPED WITH SUCH A FUSELAGE PIECE |
| DE102014112311A1 (en) * | 2014-08-27 | 2016-03-03 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Method and mold for infusing a matrix material |
| CN106738545B (en) * | 2016-12-23 | 2018-12-11 | 湘潭电机股份有限公司 | A kind of motor stator core casting Combined internal mold cored structure that can radially demould |
| CN110217405A (en) * | 2019-05-17 | 2019-09-10 | 陕西飞机工业（集团）有限公司 | A kind of aircraft delivery device installation method |
| CN110884170A (en) * | 2019-09-29 | 2020-03-17 | 广东宝通玻璃钢有限公司 | Fiber continuous winding reinforced thermoplastic pipe, manufacturing system and method thereof |
| CN110884166A (en) * | 2019-09-29 | 2020-03-17 | 广东宝通玻璃钢有限公司 | Fiber reinforced thermoplastic pipe, manufacturing system and method thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2156728A (en) * | 1984-04-05 | 1985-10-16 | Hubbell Inc Harvey | Producing an insulated connection between electrical cables |
| CN101223024A (en) * | 2005-07-15 | 2008-07-16 | 歌美飒创新技术公司 | Method of producing large hollow parts based on composite materials |
| CN101365579A (en) * | 2005-12-20 | 2009-02-11 | 空中客车法国公司 | Method of manufacturing a composite aircraft fuselage |
Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2716020C3 (en) * | 1977-04-09 | 1981-02-12 | Siempelkamp Giesserei Gmbh & Co, 4150 Krefeld | Device for applying circumferential prestress to a cylindrical container, in particular to a nuclear reactor pressure vessel |
| DE2716070C3 (en) | 1977-04-09 | 1983-06-16 | Heinrich Schlick KG, GmbH & Co, 4402 Greven | Device for clearing deposited abrasive |
| JPS6430735A (en) * | 1987-07-27 | 1989-02-01 | Sekisui Chemical Co Ltd | Method for forming reinforced resin tubular body |
| GB2259665A (en) * | 1991-09-17 | 1993-03-24 | Ford Motor Co | Moulding a reinforced plastics component |
| US20020112919A1 (en) * | 2000-12-22 | 2002-08-22 | Graham Thomas E. | Ladder tree stand |
| US7204951B2 (en) * | 2002-07-30 | 2007-04-17 | Rocky Mountain Composites, Inc. | Method of assembling a single piece co-cured structure |
| US7048024B2 (en) * | 2003-08-22 | 2006-05-23 | The Boeing Company | Unidirectional, multi-head fiber placement |
| JP2005132078A (en) * | 2003-10-28 | 2005-05-26 | Teruo Ozaki | Cylinder made of glass fiber-reinforced plastic material and method for molding hollow object having three-dimensional free surface |
| FR2870776A1 (en) * | 2004-05-28 | 2005-12-02 | Laurent Tournier | Manufacturing procedure for long components such as masts and spars from composition materials uses mould of extruded sections, especially of aluminium alloy |
| ITTO20060463A1 (en) * | 2006-06-23 | 2007-12-24 | Alenia Aeronautica Spa | EQUIPMENT AND PROCEDURE FOR THE MANUFACTURE OF A FUSELAGE TRUNK |
| US20080245929A1 (en) | 2006-10-06 | 2008-10-09 | The Boeing Company | Systems and Methods for Fabricating Multi-Material Joining Mechanisms |
| DE102007060029A1 (en) | 2007-12-13 | 2009-06-18 | Airbus Deutschland Gmbh | Method and device for producing tubular structural components |
| US8454870B2 (en) | 2008-12-19 | 2013-06-04 | The Boeing Company | Manufacturing one-piece composite sections using outer mold line tooling |
-
2010
- 2010-11-19 DE DE102010051739A patent/DE102010051739B3/en not_active Expired - Fee Related
-
2011
- 2011-11-16 US US13/883,804 patent/US9180638B2/en not_active Expired - Fee Related
- 2011-11-16 WO PCT/EP2011/070212 patent/WO2012066017A1/en active Application Filing
- 2011-11-16 EP EP11784997.6A patent/EP2640567B1/en not_active Not-in-force
- 2011-11-16 CN CN201180055371.4A patent/CN103221200B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2156728A (en) * | 1984-04-05 | 1985-10-16 | Hubbell Inc Harvey | Producing an insulated connection between electrical cables |
| CN101223024A (en) * | 2005-07-15 | 2008-07-16 | 歌美飒创新技术公司 | Method of producing large hollow parts based on composite materials |
| CN101365579A (en) * | 2005-12-20 | 2009-02-11 | 空中客车法国公司 | Method of manufacturing a composite aircraft fuselage |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2640567B1 (en) | 2014-12-31 |
| US20130340927A1 (en) | 2013-12-26 |
| WO2012066017A1 (en) | 2012-05-24 |
| DE102010051739B3 (en) | 2011-12-29 |
| EP2640567A1 (en) | 2013-09-25 |
| US9180638B2 (en) | 2015-11-10 |
| CN103221200A (en) | 2013-07-24 |
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